Split-flap wing assembly for a high endurance aircraft

1. A split-flap wing assembly for a high endurance aircraft, the wing assembly comprising:

a wing including an upper surface, a lower surface with a flap frame, a camber line, and one, two or more flap sweep hinges disposed along a forward edge of the flap frame;

a flap including a control surface, an interior surface, a forward edge, and a trailing edge, and one, two or more flap hinges defining a lateral pivot axis of the flap, the pivot axis positioned at or rearward of the forward edge;

one, two or more flap sweep members having a length, each flap sweep member having a forward end attached for pivoting at one of the flap sweep hinges, and a rearward end attached pivotally to one of the flap hinges, the flap sweep members pivotable to a deployment angle, from a neutral sweep position, at which the rearward end of the flap sweep members are farther away from the camber line of the airplane wing than at the neutral position, wherein the flap has a flap deployment angle, relative to a neutral flap position, dependent in part on the deployment angle of the flap sweep member;

wherein the flap sweep member in an active position provides a slot having a gap distance between the flap frame and the forward edge of the flap, to allow airflow from along the lower surface of the wing to flow through the slot and to the interior surface of the flap.

2. The split-flap wing assembly according to claim 1 , wherein the flap pivots at a flap pivot angle around the lateral pivot axis.

3. The split-flap wing assembly according to claim 1 , wherein the gap distance of the slot increases with the increase in outward angle of the flap sweep member.

4. The split-flap wing assembly according to claim 1 , wherein when the flap is at a neutral flap position, the deployment angle of the flap is dependent only on the deployment angle of the flap sweep member.

5. The split-flap wing assembly according to claim 1 , further including a flap sweep pivoting means for pivoting the forward end of the one, two or more flap sweep members at the one, two or more flap sweep hinges.

6. The split-flap wing assembly according to claim 1 , wherein the flap can pivot to a flap pivot angle, relative to the flap sweep member, between a neutral flap position and a passive flap position at an inward angle from the neutral flap position, with the trailing edge nearer to the camber line of the airplane wing than when the flap is at the neutral flap position, wherein the flap has a deployment angle, relative to the camber line of the wing, dependent on both the deployment angle of the flap sweep member and the flap pivot angle.

7. The split-flap wing assembly according to claim 1 , further including a flap pivoting means for pivoting the flap at the flap hinges.

8. The split-flap wing assembly according to claim 1 , wherein when the lateral pivot axis of the flap is rearward of the forward edge of the flap, the gap distance of the slot increases with an increase in inward flap pivot angle.

9. The split-flap wing assembly according to claim 1 , wherein the wing includes two or more flap sweep hinges and two or more flap sweep members, the flap includes two or more flap pivot hinges positioned along opposite ends of the lateral pivot axis.

10. The split-flap wing assembly according to claim 9 , wherein the two or more flap sweep members are configured to pivot to an outward angle of up to about 60 degrees.

11. The split-flap wing assembly according to claim 1 , wherein flap is configured to pivot to an inward flap pivot angle of up to about 60 degrees.

12. The split-flap wing assembly according to claim 6 , wherein the flap can further pivot between a neutral flap position and an active flap position at an outward flap pivot angle from the neutral flap position, with the trailing edge further from the camber line of the airplane wing than when the flap is at the neutral flap position.

13. The split-flap wing assembly according to claim 1 , wherein the upper surface of the wing provides a spoiler frame, and the wing further includes a spoiler hinge disposed along a forward edge of the spoiler frame, and a spoiler that includes a control surface, an interior surface, a forward hinge edge, and a trailing edge, the spoiler hingedly connected at the forward hinge edge to the spoiler hinge for pivoting the spoiler within the spoiler frame.

14. The split-flap wing assembly according to claim 13 , wherein the spoiler is configured to pivot to an inward deployment angle of up to about 60 degrees, an outward deployment angle of up to about 60 degrees, or both.

15. The split-flap wing assembly according to claim 13 , wherein the wing includes two or more flap sweep hinges and two or more flap sweep members, the flap includes two or more flap hinges positioned along opposite ends of the lateral pivot axis.

16. The split-flap wing assembly according to claim 15 , further including a flap sweep pivoting means for pivoting the forward end of the two or more flap sweep members at the two or more flap sweep hinges.

17. The split-flap wing assembly according to claim 16 , wherein the flap can pivot to a flap pivot angle, relative to the flap sweep member, between a neutral flap position and a passive flap position at an inward angle from the neutral flap position, with the trailing edge nearer to the camber line of the airplane wing than when the flap is at the neutral flap position, wherein the flap has a deployment angle, relative to the camber line of the wing, dependent on both the deployment angle of the flap sweep member and the flap pivot angle.

18. The split-flap wing assembly according to claim 16 , wherein the two or more flap sweep members are configured to pivot to an outward angle of up to about 60 degrees.

19. The split-flap wing assembly according to claim 18 , wherein the flap is configured to pivot to an inward flap pivot angle of up to about 60 degrees, an outward flap pivot angle of up to about 60 degrees, or both.

20. A split-flap wing assembly for an aircraft, the wing assembly comprising:

a wing including an upper surface, a lower surface with a flap frame, a camber line, and one, two or more flap sweep hinges disposed along a forward edge of the flap frame;

a flap including a control surface, an interior surface, a forward edge, and a trailing edge, and one, two or more flap hinges defining a lateral pivot axis of the flap, the pivot axis positioned at or rearward of the forward edge;

one, two or more flap sweep members having a length, each flap sweep member having a forward end attached for pivoting at one of the flap sweep hinges, and a rearward end attached pivotally to one of the flap hinges, the flap sweep members pivotable to a deployment angle, from a neutral sweep position, at which the rearward end of the flap sweep members are farther away from the camber line of the airplane wing than at the neutral position, wherein the flap has a flap deployment angle, relative to a neutral flap position, dependent in part on the deployment angle of the flap sweep member;

wherein the flap sweep member in an active position provides a slot having a gap distance between the flap frame and the forward edge of the flap, to allow airflow from along the lower surface of the wing to flow through the slot and to the interior surface of the flap.